Numerical investigation of transitional shock-wave/boundary-layer interaction in supersonic regime
We perform direct numerical simulations of shock-wave/boundary-layer interactions at Mach number M = 1.7 to investigate the influence of the state of the incoming boundary layer. The flow configuration includes a spatially evolving laminar boundary layer that is tripped by an array of distributed roughness elements and impinged further downstream by an oblique shock wave. Four SBLI cases are considered, based on two different shock impingement locations, corresponding to transitional and turbulent interactions, and two different shock strengths (3,6 deg).